CN113071276A

CN113071276A - Flying automobile

Info

Publication number: CN113071276A
Application number: CN202110376197.9A
Authority: CN
Inventors: 邓云娣
Original assignee: Individual
Current assignee: Shanghai Xinyuncai Aviation Technology Co ltd
Priority date: 2021-04-08
Filing date: 2021-04-08
Publication date: 2021-07-06
Anticipated expiration: 2041-04-08
Also published as: CN113071276B

Abstract

The invention belongs to the technical field of automobiles, and discloses a flying automobile which comprises an automobile body, a front wing, a rear wing and a propeller, wherein the automobile body comprises a head compartment and a tail compartment; the front wings are respectively arranged on two sides of the locomotive and can be unfolded to the outside of the locomotive body or folded and stored in a locomotive carriage; the rear wings are respectively arranged on two sides of the tail of the vehicle and can be unfolded to the outside of the vehicle body or folded and stored in the tail compartment of the vehicle; the propellers are respectively arranged at the wing tips of the front wing and the rear wing, the propellers can be stored in a nose compartment along with the front wing, and the propellers can be stored in a tail compartment along with the wing; in the flight state, the propeller rotates to the first position to provide vertical lift for the hovercar, and the propeller rotates to the second position to provide horizontal power for the hovercar. The invention has compact structure and large available space of the vehicle body, can be parked in a common parking space and normally run on a common road, and can vertically take off and land like a multi-rotor aircraft and fly at high speed like a fixed-wing aircraft.

Description

Flying automobile

Technical Field

The invention relates to the technical field of automobiles, in particular to a flying automobile.

Background

With the progress of science and technology and the development of society, the living standard of people is greatly improved, and the requirement on traveling is higher and higher, however, as the traffic of cities, particularly large cities, is more and more congested, the time wasted by people on traffic jam is more and more increased, and how to make people travel more conveniently and more quickly. People think of developing flying cars, and the flying cars can not only run on the road like cars, but also fly in the air to avoid traffic jam on the road, and can quickly and conveniently arrive at the destination.

The invention patent with the patent number C107757273B discloses a flying automobile, which is a flying automobile with foldable wings, telescopic tail wings and single propeller propulsion, can take off and land by running in a special runway, and has great use limitation. Patent No. CN209426502U discloses a flying vehicle capable of taking off and landing vertically and flying horizontally, which has a large external shape and a weak ground driving function. The hovercar with the patent number of CN206357938U is a multi-duct fan hovercar capable of vertically taking off and landing, and because all the duct fans are arranged inside the hovercar body, more hovercar body space is occupied, and the hovercar body space utilization rate is low. The hovercar disclosed in patent No. CN204749767U is a 4-duct fan hovercar capable of taking off and landing vertically, the duct fans are arranged on two sides of the hovercar body and can be folded, the available space in the hovercar body is large, but the horizontal flying efficiency is low and the flight distance is short due to the absence of wings.

Disclosure of Invention

The invention aims to provide a flying automobile which is compact in structure and large in available space of an automobile body, can be parked in a common parking space and normally run on a common road, and can vertically take off and land like a multi-rotor aircraft and fly at high speed like a fixed-wing aircraft.

The technical scheme provided by the invention is as follows:

a flying automobile comprising:

the vehicle body comprises a vehicle head compartment arranged at the vehicle head and a vehicle tail compartment arranged at the vehicle tail;

the two pairs of front wings are respectively arranged on two sides of the locomotive and can be unfolded to the outside of the locomotive body or folded and stored in the locomotive carriage;

the two rear wings are respectively arranged on two sides of the tail of the vehicle and can be unfolded to the outside of the vehicle body or folded and stored in the tail compartment of the vehicle;

the propellers are respectively arranged at the wing tips of the front wing and the rear wing and used for providing power for the hovercar, at least one propeller is stored in the head compartment, and at least one propeller is stored in the tail compartment;

and in the flying state, the propeller rotates to the first position to provide vertical lift force for the hovercar, and the propeller rotates to the second position to provide horizontal power for the hovercar.

Among this technical scheme, through utilizing collapsible compactness characteristics based on the structure, set up storage space in locomotive railway carriage or compartment and rear of a vehicle railway carriage or compartment department, make hovercar can freely switch over at automobile state and aircraft state, utilize the great specific power of unit mass ratio of motor and the characteristics of nimble installation arrangement, through the screw that verts, make hovercar both can take off perpendicularly and descend, but normal level flight again improves hovercar's use flexibility, promote speed and increase journey simultaneously, make hovercar have higher practical application and worth.

Further preferably, the folding device further comprises a folding mechanism, and the front wing and the rear wing are respectively connected with the vehicle body through the folding mechanism so as to be capable of being unfolded or folded for storage;

the folding mechanism comprises a first supporting seat, a first connecting piece, a second supporting seat, a telescopic piece and a guide rod, wherein the first supporting seat is fixedly arranged at the frame of the head carriage or the tail carriage, one end of the first connecting piece is hinged to the first supporting seat, the other end of the first connecting piece is fixedly connected with the wing root of the front wing or the rear wing, the second supporting seat is fixedly arranged on the bottom surface of the head carriage or the tail carriage, one end of the telescopic rod is hinged to the second supporting seat, the other end of the telescopic rod is hinged to one end of the guide rod, and the other end of the guide rod is hinged to the wing root of the front wing or the rear wing.

Further preferably, two side walls of the front carriage or the rear carriage along the length direction of the car body are respectively provided with a side plate extending towards the center line of the car body, the first support seat is arranged on one side of the side plate far away from the bottom surface of the front carriage, the second support seat is arranged on the bottom surface of the front carriage or the rear carriage, when the front wing or the rear wing is folded and stored, the telescopic rod is positioned below the front wing or the rear wing, and the guide rod is positioned below the side plate and has an included angle smaller than 90 degrees with the telescopic rod.

Further preferably, the front wing comprises a plurality of front wing boxes, and the plurality of front wing boxes are connected in a foldable manner; the rear wing comprises a plurality of rear wing boxes which are connected in a foldable mode.

Further preferably, the connecting mechanism comprises a hinge piece, a locking piece and a locking groove piece;

the front wing comprises a first front wing box and a second front wing box;

the wing tip of first preceding wing box passes through with the wing root of wing box before the second the articulated elements is connected, the locked groove spare sets up the wing tip department of first preceding wing box, the retaining member sets up the wing root department of wing box before the second, wing box is relative before the second when first preceding wing box expandes, the retaining member stretches into in the locked groove spare and with locked groove spare locking.

Further preferably, the aircraft wing further comprises a rotating mechanism, the front wing further comprises a third front wing box, a wing root of the third front wing box is connected with a wing tip of the first front wing box in a rotating mode through the rotating mechanism, a wing tip of the third front wing box is connected with a wing root of the second front wing box in a foldable mode, the propeller is fixedly arranged at the wing tip of the second front wing box, a blade rotating plane of the propeller is perpendicular to a wing surface of the second front wing box, and the third front wing box, the second front wing box and the propeller are driven to rotate together when the rotating mechanism rotates, so that the propeller is switched between the first position and the second position.

Further preferably, rotary mechanism includes driving piece, first pivot, first gear, second pivot and second gear, the driving piece the first pivot with first gear all sets up in the wing box of first preceding wing, the driving piece drive first pivot rotates, first gear sets up in the first pivot and along with first pivot rotates, the one end of second pivot with wing box fixed connection before the third, the other end of second pivot stretches into in the wing box of first preceding wing, the second gear sets up in the second pivot and with first gear engagement.

Further preferably, the aircraft further comprises a rotating mechanism, the propeller is connected with the wingtip of the second front wing box through the rotating mechanism, and the rotating mechanism drives the propeller to rotate relative to the second front wing box so as to enable the propeller to be switched between the first position and the second position.

Further preferably, the vehicle further comprises a power system, a driving shaft for driving front wheels and/or rear wheels to rotate is arranged below the vehicle body, and the power system is used for driving the propeller and the driving shaft to rotate.

Further preferably, the power system comprises a battery assembly and an electric motor, the battery assembly is arranged below a passenger compartment on the vehicle body, the battery assembly is electrically connected with the electric motor, and the electric motor is respectively in driving connection with the driving shaft and the propeller.

Further preferably, the power system comprises a battery assembly, an electric motor and an engine, the battery assembly is arranged below the passenger compartment, the engine is arranged below the head compartment or the tail compartment, the battery assembly is electrically connected with the electric motor, the electric motor is in driving connection with the propeller, and the engine is in driving connection with the driving shaft.

Further preferably, the power system comprises a battery assembly, an electric motor, an engine and a generator, the battery assembly is arranged below the passenger compartment, the engine and the generator are both arranged below the vehicle head compartment, the generator is in driving connection with the engine, the generator is electrically connected with the battery assembly, and the electric motor is in driving connection with the propeller and the driving shaft.

Further preferably, the power system further comprises a planetary gear set, the planetary gear set comprises a sun gear, a planet carrier and a gear ring, the sun gear is located at the center of the gear ring, the planet gear is located between the gear ring and the sun gear and is respectively meshed with the gear ring and the sun gear, the planet carrier is connected with the planet gear, and the sun gear, the gear ring and the planet carrier are all coaxially arranged;

the sun gear is in driving connection with the engine, the planet carrier is in driving connection with the driving shaft, and the gear ring is in driving connection with the generator; or;

the sun gear is in driving connection with the engine, the planet carrier is in driving connection with the generator, and the gear ring is in driving connection with the driving shaft; or

The sun gear is in driving connection with the driving shaft, the planet carrier is in driving connection with the engine, and the gear ring is in driving connection with the generator; or;

the sun gear is in driving connection with the driving shaft, the planet carrier is in driving connection with the generator, and the gear ring is in driving connection with the engine; or;

the sun gear is in driving connection with the generator, the planet carrier is in driving connection with the driving shaft, and the gear ring is in driving connection with the engine; or;

the sun gear is in driving connection with the generator, the planet carrier is in driving connection with the engine, and the gear ring is in driving connection with the driving shaft.

Further preferably, the planetary gear set further includes a first locker, a second locker, and a third locker, the first locker being connected to a rotating shaft of the engine, the second locker being connected to a rotating shaft of the generator, and the third locker being connected to the driving shaft.

Further preferably, in a flight state, the third locker is locked, the first locker and the second locker are unlocked, the engine drives the generator to generate electricity through the planetary gear set and transmits the electricity to the battery pack, and the motor drives the propeller to work;

when the vehicle runs on the ground, the first locker is locked, the second locker and the third locker are unlocked, and the generator drives the driving shaft to work through the planetary gear set; or;

when the vehicle runs on the ground, the second locker is locked, the first locker and the third locker are released, and the engine drives the driving shaft to work through the planetary gear set; or;

when the vehicle runs on the ground, the first locker, the second locker and the third locker are released, and the generator and the engine jointly drive the driving shaft to work through the planetary gear set; or;

when the vehicle runs on the ground, the first locker, the second locker and the third locker are released, the engine drives the generator and the driving shaft to work through the planetary gear set, and the generator generates power and transmits the power to the battery pack for storage.

Further preferably, the automobile tail assembly further comprises a tail system, wherein the tail system comprises a vertical tail, a horizontal tail and a control mechanism, the vertical tail is arranged in the automobile tail compartment, the horizontal tail is arranged at the top of the vertical tail through the control mechanism, and the control mechanism controls the horizontal tail to rotate relative to the vertical tail.

Further preferably, the horizontal rear wing includes a first horizontal rear wing and a second horizontal rear wing, the first horizontal rear wing is disposed on the top of the vertical rear wing, and the second horizontal rear wing is disposed on both sides of the first horizontal rear wing and can be unfolded or folded.

Further preferably, the empennage system further comprises an empennage retraction and release mechanism, the empennage retraction and release mechanism comprises a telescopic cylinder, a first support shaft, a second support shaft, a first lock pin and a second lock pin, one end of the telescopic cylinder is connected with the interior of the trunk, and the other end of the telescopic cylinder is hinged with the vertical empennage;

a first guide rail and a second guide rail which extend along the length direction of the car body are arranged in the car tail compartment, the second guide rail comprises a first section and a second section which are connected with each other, the second section is far away from the car head compartment and extends out of the end part of the first guide rail, and the second section is an arc-shaped track;

one end of the first supporting shaft is connected with the bottom of the vertical tail wing, and the other end of the first supporting shaft is movably arranged in the first guide rail;

one end of the second support shaft is connected with the bottom of the vertical tail wing, and the other end of the second support shaft is movably arranged in the second guide rail;

the first locking pin is arranged at one end, far away from the telescopic cylinder, of the first guide rail and used for locking the first support shaft;

the second lock pin is arranged at one end, far away from the telescopic cylinder, of the second guide rail and used for locking the second support shaft.

Further preferably, the vehicle body further comprises a parachute system, and the parachute system is arranged on the top of the passenger compartment of the vehicle body.

Further preferably, the vehicle further comprises an airbag system, and the airbag system is arranged at the bottom of the vehicle body.

The invention has the technical effects that:

(1) the front wing is arranged at the head of the vehicle, the rear wing is arranged at the tail of the vehicle, when the hovercar runs on the ground, the propellers on the front wing and the front wing can be contained in the head carriage, and the propellers on the rear wing and the rear wing can be contained in the tail carriage, so that the hovercar and a common car have the same shape and size, the hovercar can run on a road like a common car or be parked in a common parking space, and the containing of the front wing and the rear wing can not occupy the internal space of the body, for example, the internal space of the manned carriage can not be occupied, and the use volume of the manned carriage is improved. After the front wing, the rear wing and the propeller are unfolded, when the propeller rotates to a first position (vertically upwards), the hovercar has the maneuvering flexibility of vertical take-off and landing of the multi-rotor unmanned aerial vehicle, can vertically take off and land, and is not limited by a take-off site; when the propeller rotates to the second position (horizontally forwards), the aerocar has the high speed and the large range of the fixed-wing aircraft, can fly horizontally at high speed, and improves the maneuverability and the practicability of the aerocar.

(2) The third front wing box, the second front wing box and the propeller are driven to rotate together through the rotating mechanism, the wake flow projection area of the second front wing box on the propeller is small, the generated resistance is small, the influence on the lift force generated by the propeller is small, and the efficiency is high.

(3) The planetary gear set is arranged for power distribution and power coupling, so that the flying automobile can be freely switched among modes such as extended range type, oil-electricity simultaneous driving, pure oil driving and the like when running on the ground, the fuel efficiency is improved, and the endurance time and the endurance mileage are further improved.

(4) By arranging the empennage system, the pitching stability and the course stability of the aerocar during air flight can be greatly improved, and meanwhile, the control performance is also greatly improved, so that the aerocar is more favorable for low-altitude flight in cities.

Drawings

The invention is described in further detail below with reference to the following figures and detailed description:

FIG. 1 is a front view of a flying automobile according to a first embodiment of the present invention;

FIG. 2 is a top view of a flying automobile according to a first embodiment of the present invention;

FIG. 3 is a side view of a flying automobile according to a first embodiment of the present invention;

FIG. 4 is a side view of a flying automobile according to a first embodiment of the invention on the ground ready for wing deployment;

FIG. 5 is a side view of an aircraft in a takeoff state according to a first embodiment of the invention;

FIG. 6 is a front view of an aircraft according to a first embodiment of the invention;

FIG. 7 is a top view of a flying vehicle according to a first embodiment of the present invention;

FIG. 8 is a schematic view of the folding mechanism of the present invention in a folded position;

FIG. 9 is a schematic view of the folding mechanism of the present invention in an unfolded state;

FIG. 10 is a schematic view of the connection mechanism of the present invention in a folded state;

FIG. 11 is a schematic view of the connection mechanism of the present invention in a deployed state;

FIG. 12 is a front view of an hovercar as constructed in accordance with the first embodiment of the invention in a takeoff state with a third front wing box;

FIG. 13 is a top plan view of the hovercar of FIG. 12 in a takeoff condition;

FIG. 14 is a front view of the hovercar of the first embodiment of the invention in a horizontal flight state with a third front wing box;

FIG. 15 is a top plan view of the hovercar of FIG. 14 in a level flight configuration;

fig. 16 is a front view of a rotary mechanism of the present invention;

fig. 17 is a top view of a rotary mechanism of the present invention;

FIG. 18 is a powertrain layout view of the powertrain in a first implementation;

FIG. 19 is a powertrain layout for a second implementation of the powertrain;

FIG. 20 is a powertrain layout view of the powertrain in a third implementation;

FIG. 21 is a powertrain layout view of the powertrain in a fourth implementation;

FIG. 22 is a schematic illustration of a planetary gear set;

FIG. 23 is a front view of the hovercar parachute system as it is opened;

FIG. 24 is a side view of an aircraft airbag system as it is deployed;

FIG. 25 is a top view of a flying vehicle with a "T" tail system according to an embodiment of the present invention;

FIG. 26 is a side view of a flying vehicle with a "T" tail system according to an embodiment of the present invention;

FIG. 27 is a side view of a flying vehicle with a "T" tail system according to an embodiment of the present invention in the ground ready for wing deployment;

FIG. 28 is a top plan view of a horizontal flight state of a hovercar with a "T" tail system in accordance with an embodiment of the present invention;

FIG. 29 is a front view of a horizontal flight state of a flying vehicle with a "T" tail system according to an embodiment of the present invention;

FIG. 30 is a top plan view of a flying vehicle with a "T" shaped foldable tail system according to an embodiment of the present invention;

FIG. 31 is a front view of a horizontal flight state of a flying vehicle with a "T" shaped foldable tail system according to an embodiment of the present invention;

FIG. 32 is a top plan view of a two-wheeled hovercar with a "π" tail system in accordance with an embodiment of the present invention;

FIG. 33 is a side view of a two-wheeled hovercar with a "pi" tail system in accordance with an embodiment of the present invention;

FIG. 34 is a side view of a second embodiment of the present invention showing the horizontal flight of a flying vehicle with a "pi" tail system;

FIG. 35 is a front view of a horizontal flight state of a flying vehicle with a "pi" tail system according to an embodiment of the present invention;

FIG. 36 is a front view of a horizontal flight state of a flying vehicle with a "pi" shaped foldable tail system according to an embodiment of the present invention;

fig. 37 is a schematic view showing a retracted state of the rear wing retraction/release mechanism according to the second embodiment of the present invention;

fig. 38 is a schematic view showing the extended state of the tail retraction/release mechanism according to the second embodiment of the present invention.

The reference numbers illustrate:

10. a vehicle body; 11. a headstock; 12. a trunk; 121. a first guide rail; 122. a second guide rail; 1221. a first stage; 1222. a second stage; 13. a people carrying compartment; 14. a front wheel; 15. a rear wheel; 16. a drive shaft; 17. a cowl; 18. a tail cover; 19. a side plate;

20. a front wing; 211. a first front wing box; 212. a second front wing box; 213. a third front wing box; 22. a front wing aileron; 23. front wing trailing edge fly \ slat; 24. front wing leading edge fly \ slat;

30. a rear wing; 40. a propeller;

50. a folding mechanism; 51. a first support base; 52. a first connecting member; 53. a second support seat; 54. a telescoping member; 55. a guide bar;

60. a connecting mechanism; 61. an articulation member; 62. a locking member; 63. a keyway member;

70. a rotation mechanism; 71. a drive member; 72. a first rotating shaft; 73. a first gear; 74. a second rotating shaft; 75. a second gear;

80. a power system; 81. a battery assembly; 82. an electric motor; 83. an engine; 84. a generator; 85. a planetary gear set; 851. a sun gear; 852. a planet wheel; 853. a planet carrier; 854. a ring gear; 855. a first latch; 856. a second locker; 857. a third locker;

90. a parachute system; 100. an airbag system;

110. an empennage system; 111. a vertical tail; 1111. a vertical tail wing box; 1112. a rudder; 112. a horizontal rear wing; 1121. a first horizontal rear wing; 1122. a second horizontal rear wing; 113. a control mechanism; 1131. a first connection joint; 1132. a rotating shaft joint; 1133. a second connection joint; 1134. a pitch actuator cylinder; 114. an empennage retraction mechanism; 1141. a telescopic cylinder; 1142. a first support shaft; 1143. a second support shaft; 1144. a first lock pin; 1145. a second locking pin.

Detailed Description

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "one" means not only "only one" but also a case of "more than one".

It should be further understood that the term "and/or" as used in this specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.

In this context, it is to be understood that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, in the description of the present application, the terms "first", "second", and the like are used only for distinguishing the description, and are not intended to indicate or imply relative importance.

Example one

A flying automobile comprises a body 10, two pairs of front wings 20, two pairs of rear wings 30 and a plurality of propellers 40, wherein the body 10 comprises a head compartment 11 arranged at the head, a tail compartment 12 arranged at the tail and a manned compartment 13 arranged between the head compartment 11 and the tail compartment 12, front wheels 14, rear wheels 15 and a driving shaft 16 are arranged below the body 10, and the driving shaft 16 drives the front wheels 14 and/or the rear wheels 15 to rotate. The headstock 11 is provided with a headstock cover 17, and the headstock cover 17 can be opened forward and upward around a rotating shaft, or backward and upward around the rotating shaft, or opened at both sides around the rotating shaft. The trunk 12 is provided with a trunk lid 18, and the trunk lid 18 can be opened forward and upward around a rotation shaft, or backward and upward around the rotation shaft, or opened at both sides around the rotation shaft.

The two pairs of front wings 20 are respectively arranged on two sides of the locomotive and can be unfolded to the outside of the locomotive body 10 or folded and stored in the locomotive carriage 11; the two rear wings 30 are respectively disposed at two sides of the car tail, and can be unfolded to the outside of the car body 10 or folded to be accommodated in the car tail box 12. When the hovercar is parked in the garage, the front wings 20 are in a folded and retracted state and are placed in the head carriage 11, and the head cover 17 is also in a retracted state; the rear wings 30 are in a folded stowed position, placed in the trunk 12, and the tailgate 18 is also in a stowed position. At the moment, the appearance of the aerocar is consistent with that of a common car. When the aerocar flies horizontally in the air, the front wing 20 and the rear wing 30 provide lift and control moment.

The propellers 40 are respectively arranged at the wing tips of the front wing 20 and the rear wing 30 and used for providing power for the hovercar, the propellers 40 arranged on the front wing 20 can be stored in the head compartment 11 along with the front wing 20, and the propellers 40 arranged on the rear wing 30 can be stored in the tail compartment 12 along with the wing 30; in flight, rotation of the propeller 40 to the first position provides vertical lift to the hovercar and rotation of the propeller 40 to the second position provides horizontal power to the hovercar.

When the hovercar runs on the ground, the front wings 20, the rear wings 30 and the propellers 40 can be stored in the head carriage 11 and the tail carriage 12, so that the hovercar and a common car have the same shape and size, can run on a road like the common car or be parked in a common parking space, and cannot occupy the inner space of the manned carriage 13 on the body 10. After the wings and the propellers 40 are unfolded, when the propellers 40 rotate to a first position (vertically upwards), the hovercar has the maneuvering flexibility of vertical take-off and landing of the multi-rotor unmanned plane and is not limited by a take-off field; when the propeller 40 is rotated to the second position (horizontal forward), the hovercar may fly at high horizontal speed, with the high speed and range of the fixed wing aircraft.

In the existing flying automobile, in order to ensure the aerodynamic stability during flying, the wing layout is generally divided into two types, one type is a layout form of a sliding takeoff similar to a fixed wing aircraft, the wings are arranged on the two sides of the roof or the chassis in the middle of the automobile body 10 and can be folded and collected towards the middle of the automobile body 10, and the tail of the automobile is provided with a tail wing system which can be stretched back and forth; the other type is a layout form which can take off vertically and is similar to a multi-axis unmanned aerial vehicle, wherein the rotary wings are arranged on the periphery and can not be folded or folded to be folded at the outer side of the vehicle body 10, the wing layout is not provided, or the wings are arranged at the vehicle top and can be folded and folded towards the middle of the vehicle body 10, and the folded appearance is large and not compact.

The scheme of arranging the wings at the head and the tail of the airplane is different from the conventional fixed wing airplane layout, the problem of certain aerodynamic defects exists between the center of gravity of the flying automobile and the front and rear wings, the flying automobile belongs to static and unstable aerodynamic layout, and the balance of the flying automobile is kept by continuously adjusting the control surfaces of the front wings 20 and the rear wings 30 in the flying process, so that technicians in the field generally do not want to arrange the wings at the head and the tail of the airplane. However, with the continuous development of flight control systems, the problem of aerodynamic defects of statically unstable aerodynamic layout can be solved through statically unstable flight control systems, so that the scheme of arranging the wings at the nose and the tail of the vehicle can solve the problem of aerodynamic defects by using the statically unstable flight control systems, and the scheme of the invention is feasible and controllable.

In addition, in the invention, the rear wings 30 are folded and stored in the tail compartment 12, compared with the existing mode of folding and storing the rear wings 30 at the top of the vehicle, the center of gravity of the whole vehicle can be reduced, the air resistance is reduced, so that the flying vehicle has small driving resistance when driving at high speed in the vehicle state, and the side turning is not easy to occur due to low center of gravity when turning.

The front wing 20 and the rear wing 30 are respectively connected to the vehicle body 10 by a folding mechanism 50 so that the front wing 20 and the rear wing 30 can be unfolded or folded for storage.

As shown in fig. 8 and 9, the folding mechanism 50 includes a first support seat 51, a first connecting member 52, a second support seat 53, an expansion member 54, and a guide rod 55, the first support seat 51 is fixedly disposed at a frame of the front car 11 or the rear car 12, one end of the first connecting member 52 is hinged to the first support seat 51, the other end is fixedly connected to a wing root of the front wing 20 or the rear wing 30, the first connecting member 52 is rotatable around the first support seat 51, the second support seat 53 is fixedly disposed at a bottom surface of the front car 11 or the rear car 12, one end of the expansion member 54 is hinged to the second support seat 53, the expansion member 54 is rotatable relative to the second support seat 53, the other end of the expansion member 54 is hinged to one end of the guide rod 55, and the other end of the guide rod 55 is hinged to the wing root of the front wing 20 or the rear wing 30.

When the telescopic rod 54 extends, the guide rod 55 is driven to rotate, and when the guide rod 55 rotates, the front wing 20 is pushed to rotate around the first support seat 51, so that the front wing 20 is unfolded outwards.

Preferably, as shown in fig. 8 and 9, the side plates 19 extending towards the center line of the vehicle body 10 are respectively arranged on two side walls of the head box 11 or the tail box 12 along the length direction of the vehicle body 10, the first support seat 51 is arranged on one side of the side plate 19 away from the bottom surface of the head box 11, the second support seat 53 is arranged on the bottom surface of the head box 11 or the tail box 13, when the front wing 20 or the rear wing 30 is folded and stored, the telescopic rod 54 is positioned below the front wing 20 or the rear wing 30, and the guide rod 55 is positioned below the side plate 19 and forms an included angle with the telescopic rod 54 smaller than 90 degrees.

As shown in fig. 8 and 9, a side plate 19 is formed by extending inward a side wall of the vehicle head compartment 11, a first support seat 51 is disposed on the side plate 19, a first connecting member 52 can rotate around the first support seat 51, a second support seat 53 is disposed on a bottom surface of the vehicle head compartment 11, when the front wing 20 is folded and stored in the vehicle head compartment 11, a gap is formed between the front wing 20 and the bottom surface of the vehicle head compartment 11, an expansion link 54 is located in the gap, and a guide rod 55 is located right below the side plate 19 and has an included angle smaller than 90 degrees with the expansion link 54, so as to store the folding mechanism 50. When the front wing 20 is unfolded, the telescopic rod 54 extends and pushes the front wing 20 to rotate around the first supporting seat 51 through the guide rod 55, so that the front wing 20 is unfolded and is positioned outside the vehicle body 10.

The front wing 20 may include one or more front wing boxes, the front wing box is a main stressed structural member of the front wing, when the front wing 20 includes one front wing box, a wing root of the front wing box is connected with the vehicle body 10 through the folding mechanism 50, and the whole front wing box may be directly stored in the vehicle head compartment 11 through the folding mechanism 50 in an overturning manner.

When the front wing 20 comprises a plurality of front wing boxes, the plurality of front wing boxes can be connected in a folding manner, and when the front wing 20 is stored, the plurality of front wing boxes can be folded to reduce the volume of the front wing in the nose compartment 11. In order to fold a plurality of front wing box, two adjacent front wing box are connected by a connecting mechanism 60. As shown in fig. 10, the connection mechanism 60 may include a hinge 61, and the plurality of front wing boxes are folded by the hinge 61.

Preferably, as shown in fig. 10 and 11, the connecting mechanism 60 further includes a locker 62 and a locker 63, and the front wing 20 includes a first front wing box 211 and a second front wing box 212 which are adjacently disposed; the wing root of the first front wing box 211 is connected with the vehicle body 10, the wing tip of the first front wing box 211 is connected with the wing root of the second front wing box 212 through a hinge 61, a locking groove 63 is arranged at the wing tip of the first front wing box 211, a locking piece 62 is arranged at the wing root of the second front wing box 212, and when the second front wing box 212 is unfolded relative to the first front wing box 211, the locking piece 62 extends into the locking groove 63 and is locked with the locking groove 63 so as to fix the second front wing box 212. When the second front wing box 212 needs to be folded, the locking member 62 releases the locking with the locking groove member 63, and the second front wing box 212 is turned over with respect to the first front wing box 211 and folded together. The number of the front wing boxes of the front wing 20 can be set according to actual conditions, and the two adjacent front wing boxes can be folded and unfolded through a connecting mechanism.

As shown in fig. 7, the front wing 20 further includes a front wing flap 22, a front wing trailing edge flap/slat 23, and a front wing leading edge flap/slat 24, the front wing flap 22 is installed at a position close to the outer side of the trailing edge of the whole front wing box, the front wing trailing edge flap/slat 23 is installed at a position of the trailing edge of the first front wing box 211, and the front wing leading edge flap/slat 24 is installed at a position of the leading edge of the first front wing box 211 and/or a position of the leading edge of the second front wing box 212.

Each front wing 20 and each rear wing 30 are provided with a propeller 40 at the wing tip, for example, the front wing 20 includes a first front wing box 211 and a second front wing box 212, the first front wing box 211 is connected with the vehicle body 10, and the propeller 40 is provided at the wing tip of the second front wing box 212. The propeller 40 may be a shafted propeller, or a ducted shaftless propeller, or a single propeller, or a twin-propeller counter-rotating propeller. The propeller blades are two or more. The blades of the propeller 40 are foldable, and when the front wing 20 and the rear wing 30 are folded, the blades of the propeller 40 are folded; when the front wing 20 and the rear wing 30 are deployed, the blades of the propeller 40 are deployed.

When the propeller 40 is disposed at the wing tip of the second front wing box 212, the propeller 40 may be connected to the second front wing box 212 through the rotating mechanism 70, and the rotating mechanism 70 drives the propeller 40 to rotate relative to the second front wing box 212, so that the propeller 40 is switched between the first position (vertically upward) and the second position (horizontally forward). When the hovercar needs to take off, the propeller 40 rotates to the vertical upward position to provide vertical upward power for the hovercar, so that the hovercar can take off vertically. In the scheme, the rotating mechanism is arranged close to the propeller, the bending load generated by the lifting force of the propeller at the rotating mechanism is small, the motor can be directly rotated, and the structure is relatively simple and light. However, as shown in fig. 7, when the propeller 40 is vertically upward, the second front wing box 212 is located below a part of the blades of the propeller 40, and the wake flow of the propeller 40 is mostly blocked by the airfoil surface of the second front wing box 212, the generated drag is large, the lift force generated by a part of the propeller 40 is offset, and the efficiency is reduced.

In order to solve the problem that the wake flow of the propeller 40 is blocked by the second front wing box 212, as shown in fig. 12 to 15, the front wing 20 further includes a third front wing box 213, a wing root of the third front wing box 213 is rotatably connected to a wing tip of the first front wing box 211 through a rotating mechanism 70, a wing tip of the third front wing box 213 is foldably connected to a wing root of the second front wing box 212 through a folding mechanism 50, the propeller 40 is fixedly disposed at the wing tip of the second front wing box 212 and a blade rotating plane of the propeller 40 is perpendicular to a wing surface of the second front wing box 212, and the rotating mechanism 70 drives the third front wing box 213, the second front wing box 212 and the propeller 40 to rotate together when rotating, so that the propeller 40 is switched between the first position and the second position. When the front wing 20 includes more than three front wing boxes, the third front wing box 213 is disposed between the last front wing box (the front wing box connected to the propeller 40) and the penultimate front wing box.

As shown in fig. 12 and 13, when the rotating mechanism 70 drives the third front wing box 213, the second front wing box 212 and the propeller 40 to rotate together until the propeller 40 is vertically upward (the first position), the blade rotation plane of the propeller 40 is parallel to the horizontal plane, the airfoil surface of the second front wing box 212 is perpendicular to the horizontal plane, and the wake flow projection area of the second front wing box 212 on the propeller 40 is small, the streamline is good, the generated resistance is small, the influence on the lift force generated by the propeller 40 is small, and the efficiency is high. As shown in fig. 14 and 15, when the rotating mechanism 70 drives the third front wing box 213, the second front wing box 212, and the propeller 40 to rotate together until the propeller 40 is horizontally forward, the rotation plane of the propeller 40 is perpendicular to the horizontal plane, and the airfoil surface of the second front wing box 212 and the airfoil surface of the first front wing box 211 are both horizontally disposed.

As shown in fig. 16 and 17, the rotating mechanism 70 includes a driving member 71, a first rotating shaft 72, a first gear 73, a second rotating shaft 74 and a second gear 75, the driving member 71, the first rotating shaft 72 and the first gear 73 are all disposed in the first front wing box 211, the first rotating shaft 72 is connected to the first front wing box 211 through a bearing, the driving member 71 drives the first rotating shaft 72 to rotate, the first gear 73 is disposed on the first rotating shaft 72 and rotates with the first rotating shaft 72, one end of the second rotating shaft 74 is fixedly connected to the third front wing box 213, the other end of the second rotating shaft 74 extends into the first front wing box 211, the second rotating shaft 74 is connected to the first front wing box 211 through a bearing, and the second gear 75 is disposed on the second rotating shaft 74 and is meshed with the first gear 73.

The driving member 71 drives the first rotating shaft 72 to rotate, the first rotating shaft 72 drives the first gear 73 to rotate, the first gear 73 drives the second gear 75 to rotate, the second gear 75 drives the second rotating shaft 74 to rotate, and the second rotating shaft 74 drives the third front wing box 213 to rotate when rotating.

The folding mechanism 50, the connecting mechanism 60, and the rotating mechanism 70 can also be applied to the rear wing 30, and the structure and function of the rear wing 30 can be the same as those of the front wing 20, and will not be described herein again.

To ensure proper operation of the hovercar, the hovercar further includes a power system 80, the power system 80 being adapted to drive the rotation of the propeller 40 and the drive shaft 16. Among other things, the powertrain 80 has multiple implementations.

In a first implementation, as shown in fig. 18, the power system 80 is in a pure electric mode, the power system 80 includes a battery assembly 81 and a motor 82, the battery assembly 81 is disposed below the passenger compartment 13, the battery assembly 81 is electrically connected to the motor 82, and the motor 82 is in driving connection with the driving shaft 16 and the propeller 40, respectively. The number of the motors 82 is four or more, wherein one or two sets of the motors 82 are in driving connection with the driving shaft 16, one or more sets of the motors 82 are in driving connection with the propeller 40 respectively, and the propeller 40, the front wheels 14 and/or the rear wheels 15 are driven to rotate by the motors 82. The motor 82 may be a dc motor, or a synchronous motor, or an ac motor, etc. The type or number of motors 82 may be set according to actual requirements. The motor 82 that drives the front and rear wheels may be disposed below the head box 11 or the tail box 12, and the motor that drives the propeller 40 may be disposed at the front wing 20 and the rear wing 30 and connected to the propeller 40. The battery of the battery assembly 81 may be a lithium battery, or a lithium iron phosphate battery, or a nickel metal hydride battery, or a nickel cadmium battery, or a fuel cell, or a solar cell. The battery assembly 81 provides electrical power to the motor 82. The purely electric power scheme saves complex systems such as an engine, a gearbox and the like, so that the power system 80 is simple, the cost is reduced, and the space can be saved, so that the front wing and the rear wing can be conveniently stored.

In a second implementation, as shown in fig. 19, the power system 80 is in a hybrid power mode, the power system 80 includes a battery assembly 81, an electric motor 82 and an engine 83, the battery assembly 81 is disposed below the passenger compartment 13, the engine 83 is disposed below the head compartment 11 or the tail compartment 12, the battery assembly 81 is electrically connected to the electric motor 82, the electric motor 82 is in driving connection with the propeller 40, and the engine 83 is in driving connection with the driving shaft 16. When the flying vehicle travels on the road surface, the drive shaft 16 is driven by the engine 83 to operate, and when the flying vehicle flies, the propeller 40 is driven by the motor 82 to operate. The engine 83 may be a piston engine or a jet engine. The power scheme is that a set of power system 80 similar to an electric multi-rotor unmanned aerial vehicle is added on the basis of a common fuel vehicle, the modification amount is small, the scheme is simple, and in the scheme, because the engine 83 is added, the height of the head compartment 11 or the tail compartment 12 needs to be increased a little bit in order to accommodate the front wing 20 or the rear wing 30.

In a third implementation, as shown in fig. 20, the power system 80 includes a battery assembly 81, a motor 82, an engine 83, and a generator 84, the battery assembly 81 is disposed below the passenger compartment 13, the engine 83 and the generator 84 are both disposed below the vehicle cabin 11, the generator 84 is in driving connection with the engine 83, the generator 84 is electrically connected with the battery assembly 81, and the motor 82 is in driving connection with the propeller 40 and the drive shaft 16. The engine 83 drives the generator 84 to generate electric power, and stores the electric power in the battery assembly 81. In the scheme, on the basis of a pure electric power scheme, the engine 83 and the generator 84 are additionally arranged to charge the battery, the characteristic of high energy density of gasoline/diesel oil is fully utilized, the weight of the battery pack is reduced, and the endurance time and the endurance mileage are improved. The generator 84 may be a generator/motor combination.

A fourth implementation manner, as shown in fig. 21, based on the third implementation manner, the power system 80 further includes a planetary gear set 85, as shown in fig. 22, the planetary gear set 85 includes a sun gear 851, a planetary gear 852, a planet carrier 853, and a ring gear 854, the sun gear 851 is located at the center of the ring gear 854, the planetary gear 852 is located between the ring gear 854 and the sun gear 851 and respectively meshed with the ring gear 854 and the sun gear 851, the planet carrier 853 is connected with the planetary gear 852, and the sun gear 851, the ring gear 854, and the planet carrier 853 are all coaxially;

sun gear 851 is drivingly connected to engine 83, carrier 853 is drivingly connected to drive shaft 16, and ring gear 854 is drivingly connected to generator 84; or;

sun gear 851 is drivingly connected to engine 83, carrier 853 is drivingly connected to generator 84, and ring gear 854 is drivingly connected to drive shaft 16; or

Sun gear 851 is drivingly connected to drive shaft 16, carrier 853 is drivingly connected to the rotating shaft of engine 83, and ring gear 854 is drivingly connected to generator 84; or;

sun gear 851 is drivingly connected to drive shaft 16, carrier 853 is drivingly connected to generator 84, and ring gear 854 is drivingly connected to engine 83; or;

sun gear 851 is drivingly connected to generator 84, carrier 853 is drivingly connected to drive shaft 16, and ring gear 854 is drivingly connected to engine 83; or;

sun gear 851 is drivingly connected to generator 84, carrier 853 is drivingly connected to engine 83, and ring gear 854 is drivingly connected to drive shaft 16.

By arranging the planetary gear set 85 to carry out power distribution and power coupling, when the flying automobile runs on the ground, the modes of range extension, oil-electricity simultaneous driving, pure oil driving and the like can be freely switched, the fuel efficiency is improved, and the endurance time and the endurance mileage are further improved.

Preferably, as shown in fig. 22, in the fourth implementation, the planetary gear set 85 further includes a first locker 855, a second locker 856 and a third locker 857, the first locker 855 is connected to a rotating shaft of the engine 83, the second locker 856 is connected to a rotating shaft of the generator 84, and the third locker 857 is connected to the driving shaft 16. The first locker 855, the second locker 856, and the third locker 857 may be used to control whether the engine 83, the generator 84, and the drive shaft 16 are operated, respectively.

In the flying state, the third locker 857 is locked, the first locker 855 and the second locker 856 are unlocked, the driving shaft 16 is not operated, the engine 83 drives the generator 84 to generate electricity through the planetary gear set 85 and transmit the electricity to the battery assembly 81, the battery assembly 81 distributes the electricity to the motors 82 at the front wing 20 and the rear wing 30, the motors 82 drive the propellers 40 to work, and the propellers 40 generate downward thrust to push the hovercar to vertically take off or land or generate backward thrust to push the hovercar to horizontally fly.

In the ground pure electric driving state, the first locker 855 is locked, the second locker 856 and the third locker 857 are released, at this time, the engine 83 does not work, the generator 84 is in a motor mode, the generator 84 drives the driving shaft 16 to work through the planetary gear set 85, and the driving shaft 16 drives the front wheels 14 and/or the rear wheels 15 to rotate, so that the hovercar can normally drive.

In a ground pure oil running state, the second locker 856 is locked, the first locker 855 and the third locker 857 are released, the generator 84 does not work, the engine 83 works, the engine 83 drives the driving shaft 16 to work through the planetary gear set 85, and the driving shaft 16 drives the front wheels 14 and/or the rear wheels 15 to rotate, so that the hovercar runs normally.

In the ground hybrid driving state, the first locker 855, the second locker 856 and the third locker 857 are released, the generator 84 is in the motor mode, the engine 83 is operated, the generator 84 and the engine 83 jointly drive the driving shaft 16 through the planetary gear set 85 to operate, and the driving shaft 16 drives the front wheels 14 and/or the rear wheels 15 to rotate, so that the hovercar normally runs.

When the aircraft runs on the ground by pure oil and is charged, the first locker 855, the second locker 856 and the third locker 857 are released, the generator 84 works in a generator mode, the engine 83 works, the engine 83 drives the generator 84 and the driving shaft 16 to work simultaneously through the planetary gear set 85, the generator 84 generates electricity and transmits the electricity to the battery assembly 81 for storage, and the driving shaft 16 drives the front wheels 14 and/or the rear wheels 15 to rotate, so that the aircraft runs normally.

Preferably, as shown in fig. 23, the hovercar further comprises a parachute system 90, and the parachute system 90 is disposed on the top of the passenger compartment 13 of the vehicle body 10. Parachute system 90 is attached to the framework at the top of passenger compartment 13. Normally, the parachute system 90 is folded and placed at a designated position on the top of the people box 13; when the aerocar breaks down above the designated altitude in the air and can not normally fly, the parachute system 90 is opened to assist the aerocar to safely land on the ground through the air resistance.

As shown in fig. 24, the flying car further includes an airbag system 100, and the airbag system 100 is disposed at the bottom of the car body 10 and connected to the underbody frame of the car body 10. Under normal conditions, the emergency landing airbag system 100 is folded and placed at a designated position at the bottom of the vehicle body 10; when the flying automobile fails to fly normally under the designated altitude in the air or during the taking-off and landing processes, the emergency landing airbag system 100 is rapidly opened, and the flying automobile can land on the ground safely by absorbing the impact energy when the flying automobile impacts the ground.

When the flying automobile exits from a garage and enters a common road to run, the flying automobile is in a pure electric running state when being started and in a low-speed state, the first locker 855 is locked, the second locker 856 and the third locker 857 are released, the engine 83 does not work, the generator 84 works in a motor mode, the generator 84 drives the driving shaft 16 to rotate through the planetary gear set 85, and the driving shaft 16 drives the front wheel 14 to rotate; in the middle-high speed driving state, the first locker 855, the second locker 856 and the third locker 857 are all released, the engine 83 is operated, the generator 84 is operated in the generator mode, the engine 83 simultaneously drives the generator 84 and the driving shaft 16 to operate through the planetary gear set 85, the generator 84 generates electricity to be transmitted to the battery assembly 81 for storage, and the driving shaft 16 drives the front wheels 14 to rotate.

When the hovercar is ready to take off and take off vertically on the ground, the headstock cover 17 and the tailstock cover 18 are opened, the folding mechanism 50 drives the first front wing box 211 and the second front wing box 212 to be unfolded towards two sides in sequence, then the blades of the propeller 40 are unfolded to a normal state, the rotating mechanism 70 drives the propeller 40 to rotate backwards and upwards to a vertically upward state, and then the headstock cover 17 and the tailstock cover 18 are closed; the third locker 857 is locked, the first locker 855 and the second locker 856 are unlocked, the engine 83 is operated, the generator 84 is operated in a generator mode, the engine 83 drives the generator 84 to operate through the planetary gear set 50, and the generator 84 generates electricity and transmits the electricity to the battery assembly 81 for storage; the battery assembly 81 transmits electrical energy to the motor 82, the motor 82 drives the propeller 40 to rotate, and the propeller 40 generates pulling force to enable the aerocar to take off vertically.

When the aerocar flies from vertical to horizontal, the rotating mechanism 70 drives the propeller 40 to deflect forwards gradually from a vertical upward state until the propeller 40 deflects to a horizontal forward state, and at the moment, the aerocar is in a normal horizontal flying state.

When the aerocar vertically lands from the horizontal flying state, the rotating mechanism 70 drives the propeller 40 to gradually deflect backwards and upwards from the horizontal forward state until the propeller 40 deflects to the vertical upward state, and at the moment, the aerocar gradually turns to the hovering state from the horizontal flying state until the aerocar lands on the ground.

When the hovercar enters a normal road to travel to a destination after vertically landing, the rotating mechanism 70 drives the propeller 40 to rotate forwards to a horizontal forward state, the blades of the propeller 40 are folded to a folded state, then the head cover 17 and the tail cover 18 are opened, the folding mechanism 50 drives the first front wing box 211 and the second front wing box 212 to be sequentially folded and to be packed in the head box 11, the folding mechanism 50 drives the first rear wing box and the second rear wing box to be sequentially folded and to be packed in the tail box 12, and then the head cover 17 and the tail cover 18 are closed; the mode of the hovercar driving to the destination on the common road is consistent with the mode of the hovercar driving out of the garage and the hovercar driving on the common road, and the description is omitted.

When the aerocar fails to fly in the flying process or in the vertical takeoff and landing process, if the flying height reaches the designated height at which the parachute system 90 can be opened, the parachute system 90 is opened, so that the aerocar slowly slides to land on the ground; if the flying height is lower than the designated height at which the parachute system 90 can be opened, when the flying automobile falls to the designated height at which the emergency landing airbag system 100 is opened, the emergency landing airbag system 100 is released and is arranged between the flying automobile and the ground to absorb the impact energy when the flying automobile impacts the ground, so that the flying automobile safely lands on the ground, and the safety of personnel and vehicles is protected.

Example two

The present embodiment is added with the empennage system on the basis of the first embodiment, and the same points in the present embodiment as those in the first embodiment are not described herein again. As shown in fig. 25 to fig. 36, the hovercar of the present embodiment further includes a tail system 110, the tail system 110 includes a vertical tail 111, a horizontal tail 112 and a control mechanism 113, the vertical tail 111 is disposed in the trunk 12, the horizontal tail 112 is disposed on top of the vertical tail 111 through the control mechanism 113, and the control mechanism 113 controls the horizontal tail 112 to move in a pitch direction relative to the vertical tail 111.

As shown in fig. 27, the control mechanism 113 includes a first connection joint 1131, a rotation shaft joint 1132, a second connection joint 1133 and a pitch actuator 1134, one end of the first connection joint 1131 is fixedly connected to the horizontal tail 112, one end of the rotation shaft joint 1132 is fixedly connected to the top of the vertical tail 111, the other end of the first connection joint 1131 is hinged to the other end of the rotation shaft joint 1132, the pitch actuator 1134 is installed on the top of the vertical tail 111, one end of the second connection joint 1133 is fixedly connected to the horizontal tail 112, and the pitch actuator 1134 is hinged to the other end of the second connection joint 1133. When the pitch actuator 1134 expands and contracts, the horizontal rear wing 112 is driven by the second connection joint 1133 to perform a pitch motion around the hinge point of the pivot joint 1132 and the first connection joint 1131.

As shown in fig. 26 and 27, the vertical tail 111 includes a vertical tail box 1111 as a main stress structure of the vertical tail 111, and a rudder 1112 installed at a rear edge of the vertical tail box 1111 to be rotatable left and right about a rotation axis. The vertical tail 111 may be a single vertical tail or a double vertical tail, and as shown in fig. 25, when the vertical tail 111 is a single vertical tail, it is called a "T" type vertical tail layout, and as shown in fig. 32, when the vertical tail 111 is a double vertical tail, it is called a "pi" type vertical tail layout.

As shown in fig. 30, 31 and 36, the horizontal rear wing 112 includes a first horizontal rear wing 1121 and a second horizontal rear wing 1122, the first horizontal rear wing 1121 is disposed on the top of the vertical rear wing 111, the second horizontal rear wing 1122 is disposed on both sides of the first horizontal rear wing 1121, and the second horizontal rear wing 1122 can be unfolded or folded toward both sides, and the second horizontal rear wing 1122 can be connected to the first horizontal rear wing 1121 through the connection mechanism in the first embodiment to be unfolded or folded.

As shown in fig. 37 and 38, the tail system 110 further includes a tail retraction mechanism 114, the tail retraction mechanism 114 includes a telescopic cylinder 1141, a first support shaft 1142, a second support shaft 1143, a first lock pin 1144 and a second lock pin 1145, one end of the telescopic cylinder 1141 is connected with the inside of the car tail compartment 12, the other end of the telescopic cylinder 1141 is hinged to the vertical tail 111, and the vertical tail 111 and the telescopic cylinder 1141 can rotate relatively.

A first guide rail 121 and a second guide rail 122 which extend along the length direction of the vehicle body 10 are arranged inside the tail compartment 12, the second guide rail 122 comprises a first section 1221 and a second section 1222 which are connected with each other, the first section 1221 is arranged close to the head compartment 11, the second section 1222 is arranged far away from the head compartment 11 and extends out of the end part of the first guide rail 121, the second section 1222 is an arc-shaped rail, namely the first section 1221 and the second section 1222 are sequentially arranged along the direction from the head compartment 11 to the tail compartment 12, the first section 1221 and the first guide rail 121 can be arranged in parallel, and the second section 1222 is bent along the direction close to the first guide rail 121; one end of the first support shaft 1142 is connected to the bottom of the vertical tail 111, and the other end is movably disposed in the first guide rail 121, and the first support shaft 1142 can slide and rotate in the first guide rail 121; one end of the second supporting shaft 1143 is connected to the bottom of the vertical tail 111, and the other end is movably disposed in the second guide rail 122, and the second supporting shaft 1142 can slide and rotate in the second guide rail 122.

A first locking pin 1144 is disposed at one end of the first guide rail 121 far from the telescopic cylinder 1141, and is used for locking the first support shaft 1144, so as to fix the first support shaft 1144 at a designated position of the first guide rail 121; a second lock pin 1145 is provided at an end of the second guide rail 122 remote from the telescopic cylinder 1141 for locking the second support shaft 1145 to fix the second support shaft 1145 at a designated position of the second guide rail 122.

When the tail system 110 is in the retracted state and needs to be deployed, the telescopic cylinder 1141 is extended to push the vertical tail 111 to move backwards along the first guide rail 121 and the second guide rail 122, and when the first support shaft 1142 slides to a specified position along the first guide rail 121, the first lock pin 1144 is locked, so that the first support shaft 1142 is fixed at the specified position in the first guide rail 121. The telescopic tube 1141 continues to extend, at this time, the second support shaft 1143 continues to move along the second section 1222 of the second guide rail 122, the entire tail system 110 rotates upward around the first support shaft 1142 until the second support shaft 1143 slides to a specified position along the second section 1222 of the second guide rail 122, at this time, the second lock pin 1145 is locked, so that the second support shaft 1143 is fixed at the specified position of the second guide rail 122, the telescopic tube 1141 stops extending, and the tail system 110 is in a fully extended state.

When the tail system 110 is in the unfolded state and needs to be folded, the second locking pin 1145 is unlocked, the telescopic cylinder 1141 is contracted to pull the tail system 110 to move along the second section 1222 of the second guide rail 122 and rotate downwards around the first supporting shaft 1142 until the tail system is in the horizontal state, the first locking pin 1144 is unlocked again, at this time, the telescopic cylinder 1141 is continuously contracted, and the tail system 110 is pulled to move forwards along the first sections 1221 of the first guide rail 121 and the second guide rail 122 until the tail system 110 is in the completely contracted state, so that the tail system 110 is stored in the tail compartment 12.

The vertical rear wings 111 are installed at the middle of the trunk 12 when the rear wing system 110 is in a "T" shape layout, and the vertical rear wings 111 are installed at both sides of the trunk 12 when in a "pi" shape layout. When the tail system 110 is retracted, the tail system 110 is rotated backward and downward by a designated angle along the rotating shaft and then moved forward along the guide rail at the corresponding position of the car tail box 12 until the fully retracted state is reached. When the tail system 110 is deployed, the tail system 110 is integrally moved backward along the guide rail at the corresponding position of the trunk 12 to a designated position, and then integrally rotated forward and upward along the rotation shaft until a fully deployed state is reached.

Compared with the first embodiment, the vertical tail wing 111 and the horizontal tail wing 112 are added, so that although the overall weight of the flying automobile is increased and the effective load is reduced, the pitching stability and the course stability of the flying automobile are greatly improved during air flight, the maneuverability is also greatly improved, the low-altitude flight in cities is facilitated, and whether the tail wing system 110 is arranged or not can be selected according to requirements during actual use.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims

1. A flying automobile, comprising:

2. The flying automobile of claim 1, further comprising a folding mechanism, wherein the front wing and the rear wing are respectively connected with the automobile body through the folding mechanism, so that the front wing and the rear wing can be unfolded or folded for storage;

3. The hovercar as claimed in claim 2, wherein side plates extending towards the center line of the hovercar body are respectively arranged on two side walls of the head compartment or the tail compartment along the length direction of the hovercar body, the first supporting seat is arranged on one side of the side plate far away from the bottom surface of the head compartment, the second supporting seat is arranged on the bottom surface of the head compartment or the tail compartment, when the front wing or the rear wing is folded and stored, the telescopic rod is positioned below the front wing or the rear wing, and the guide rod is positioned below the side plate and forms an included angle smaller than 90 degrees with the telescopic rod.

4. A flying automobile according to claim 1, wherein the front wing comprises a plurality of front wing boxes, and the plurality of front wing boxes are connected in a foldable manner; the rear wing comprises a plurality of rear wing boxes which are connected in a foldable mode.

5. A flying automobile according to claim 4, further comprising an attachment mechanism comprising a hinge member, a retaining member and a keyway member;

the front wing comprises a first front wing box and a second front wing box;

6. The flying automobile of claim 5, further comprising a rotating mechanism, wherein the front wing further comprises a third front wing box, a wing root of the third front wing box is rotatably connected with a wing tip of the first front wing box through the rotating mechanism, a wing tip of the third front wing box is foldably connected with a wing root of the second front wing box, the propeller is fixedly arranged at the wing tip of the second front wing box, a blade rotating plane of the propeller is perpendicular to a wing surface of the second front wing box, and the rotating mechanism drives the third front wing box, the second front wing box and the propeller to rotate together to switch the propeller between the first position and the second position.

7. A flying car according to claim 6,

the rotary mechanism comprises a driving piece, a first rotating shaft, a first gear, a second rotating shaft and a second gear, the driving piece is arranged on the first rotating shaft and the first gear is arranged in the first front wing box, the driving piece drives the first rotating shaft to rotate, the first gear is arranged on the first rotating shaft and rotates along with the first rotating shaft, one end of the second rotating shaft is fixedly connected with the third front wing box, the other end of the second rotating shaft extends into the first front wing box, and the second gear is arranged on the second rotating shaft and is meshed with the first gear.

8. The flying automobile of claim 5, further comprising a rotating mechanism, wherein the propeller is connected with the wing tip of the second front wing box through the rotating mechanism, and the rotating mechanism drives the propeller to rotate relative to the second front wing box so as to switch the propeller between the first position and the second position.

9. A flying car according to any one of claims 1 to 8, further comprising a power system, wherein a drive shaft is arranged below the car body for driving the front wheels and/or the rear wheels to rotate, and the power system is arranged for driving the propeller and the drive shaft to rotate.

10. A flying automobile according to claim 9, wherein the power system comprises a battery pack and an electric motor, the battery pack being disposed below the passenger compartment on the automobile body, the battery pack being electrically connected to the electric motor, the electric motor being drivingly connected to the drive shaft and the propeller, respectively.

11. A flying automobile according to claim 9, wherein the power system comprises a battery assembly disposed beneath the passenger compartment, an electric motor disposed beneath the head compartment or the tail compartment, the battery assembly being electrically connected to the electric motor, the electric motor being in driving connection with the propeller, and an engine in driving connection with the drive shaft.

12. A flying automobile according to claim 9, wherein the power system comprises a battery assembly, an electric motor, an engine and a generator, the battery assembly being disposed beneath the passenger compartment, the engine and the generator both being disposed beneath the head compartment, the generator being in driving connection with the engine, the generator being electrically connected to the battery assembly, and the electric motor being in driving connection with the propeller and the drive shaft.

13. A flying automobile according to claim 12, wherein the power system further comprises a planetary gear set comprising a sun gear, planet gears, a planet carrier and a ring gear, the sun gear being located at the centre of the ring gear, the planet gears being located between the ring gear and the sun gear and meshing with the ring gear and the sun gear respectively, the planet carrier being connected with the planet gears, the sun gear, the ring gear and the planet carrier being coaxially arranged;

14. A flying automobile according to claim 13, wherein the planetary gear set further comprises a first locker, a second locker and a third locker, the first locker being connected to a rotating shaft of the engine, the second locker being connected to a rotating shaft of the generator, and the third locker being connected to the drive shaft.

15. A flying automobile according to claim 14,

in a flight state, the third locker is locked, the first locker and the second locker are released, the engine drives the generator to generate electricity through the planetary gear set and transmits the electricity to the battery assembly, and the motor drives the propeller to work;

16. A flying automobile according to claim 1, further comprising a tail system comprising a vertical tail disposed in the tail compartment, a horizontal tail disposed on top of the vertical tail via a control mechanism, and a control mechanism for controlling the rotation of the horizontal tail relative to the vertical tail.

17. A flying car as claimed in claim 16, wherein the horizontal rear wing comprises a first horizontal rear wing and a second horizontal rear wing, the first horizontal rear wing is disposed on the top of the vertical rear wing, and the second horizontal rear wing is disposed on both sides of the first horizontal rear wing and can be unfolded or folded.

18. The flying automobile of claim 16, wherein the tail system further comprises a tail retraction mechanism, the tail retraction mechanism comprises a telescopic cylinder, a first support shaft, a second support shaft, a first lock pin and a second lock pin, one end of the telescopic cylinder is connected with the interior of the tail compartment, and the other end of the telescopic cylinder is hinged with the vertical tail;

19. The flying automobile of claim 1, further comprising a parachute system disposed on top of the passenger compartment of the automobile body.

20. A flying automobile according to claim 1, further comprising an airbag system disposed at the bottom of the automobile body.